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Publication numberUS20030213227 A1
Publication typeApplication
Application numberUS 10/459,918
Publication date20 Nov 2003
Filing date11 Jun 2003
Priority date5 May 2000
Also published asUS7065957
Publication number10459918, 459918, US 2003/0213227 A1, US 2003/213227 A1, US 20030213227 A1, US 20030213227A1, US 2003213227 A1, US 2003213227A1, US-A1-20030213227, US-A1-2003213227, US2003/0213227A1, US2003/213227A1, US20030213227 A1, US20030213227A1, US2003213227 A1, US2003213227A1
InventorsRonald Balzer
Original AssigneeBalzer Ronald L.
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Segmented mixing device for jet engines and aircraft
US 20030213227 A1
Abstract
Disclosed is a means for reducing jet engine exhaust noise wherein mixing is enhanced between adjacent exhaust flows and between exhaust flow and free-stream flow. Also disclosed is a means for improving the thrust of jet engines and for reducing the noise and drag of aircraft. The device is a segmented, triangular or trapezoidal shaped, curved extension to a nozzle's sleeve or surface trailing edge that results in a serrated trailing edge. The extensions enhance the natural free mixing of the adjacent flows and therefore reduce the acoustic energy associated with the velocity differences between the streams in which they are imbedded. The novel structure forces adjacent flows to penetrate into one another to a greater depth than that achieved with free mixing and results in a more uniform flow in a shorter stream wise distance. As a result of the enhanced mixing, drag on flow surfaces that are downstream of the devices and are scrubbed by the flows adjacent to the devices can be reduced.
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Claims(8)
What is claimed is:
1. A method for creating vortexes to mix flow and reduce noise and drag from a jet engine or aircraft comprising:
a segmented nozzle or surface extension having a saw toothed planform shape with semi-round tips and valleys wherein vortexes are created by immersing the tip of the segmented nozzle or surface extension into the adjacent flow.
2. A method for utilizing segmented surface or nozzle extensions on a jet engine comprising the steps of:
utilizing axisymetric, segmented surface extensions on nozzles to reduce noise due to the adjacent flows; and,
utilizing said surface extensions to reduce drag on surfaces downstream of the segmented surface extensions when those surfaces are scrubbed by flow adjacent to the segmented surface extensions.
3. A method for utilizing segmented surface extensions on aircraft comprising the steps of:
utilizing segmented surface extensions to reduce noise due to the adjacent flows; and,
utilizing said surface extensions to reduce drag on surfaces downstream of the segmented surface extensions when those surfaces are scrubbed by flow adjacent to the segmented surface extensions.
4. In combination: a gas flow nozzle or vent; said gas flow nozzle or vent having a trailing edge; a segmented extension for said gas flow nozzle or vent; and, said extension having a saw toothed planform shape with semi-round tips and valleys for enhancing the reduction of noise due to the flow exiting the nozzle or vent and for enhancing engine thrust.
5. In combination: an aircraft; said aircraft having a wing with a slot between fore and aft airfoils; and said fore airfoil incorporating a segmented trailing edge extension such that the extension is located in said slot; and, said extension having a saw toothed planform shape with semi-round tips and valleys for enhancing the reduction of noise due to the adjacent flows and for reducing the drag and increasing the lift of the wing.
6. The combination according to claims 4 or 5 wherein said extension has a triangular planform.
7. The combination according to claims 4 or 5 wherein said extension has a trapezoidal planform.
8. The combination according to claims 4, 5, 6, or 7 wherein said extension has unequal tip and valley radii.
Description
    CROSS-REFERENCE TO RELATED APPLICATIONS
  • [0001]
    This application claims priority from application Ser. No. 10/351,649, filed Jan. 23, 2003, now pending, which claims priority from application Ser. No. 09/822,962, filed Mar. 30, 2001,now pending, which claims priority from provisional application serial No. 60/203,222, filed May 5, 2000, abandoned.
  • FIELD OF THE INVENTION
  • [0002]
    Jet engines can produce a high noise level if the velocity of the mass flow exiting the engine is non-uniform and high. For performance considerations, jet engines often have multiple nozzles with the mass flow exiting each nozzle at a different velocity. Since noise radiating from a jet's exhaust increases with the intensity and non-uniformity of the exhaust velocity, jet noise reduction concepts have historically focused on methods for rapidly mixing the flows and achieving a uniform velocity within a short distance of the nozzles.
  • BACKGROUND OF THE INVENTION
  • [0003]
    Various flow-mixing devices have been employed in the past to achieve a uniform velocity within a jet's exhaust and to reduce the noise radiated from the exhaust flow. While those devices have been successful at reducing jet noise, the thrust, drag, and weight penalty associated with those devices have often been of a magnitude that the noise at constant aircraft performance has not been reduced. During the NASA Advanced Subsonic Transport (AST) Program (reference 1) sharp pointed, triangular shaped, extensions added to the sleeve of an external plug primary nozzle were tested and were found to reduce jet noise. A. D. Young et al (U.S. Pat. No. 3,153,319, reference 2) also developed extensions that when added to the trailing edge of nozzles reduced jet noise.
  • [0004]
    The primary difference between the above-described prior art and the hereinafter described invention is the rounding of the upstream intersection of the extensions with the nozzle and the rounding of the extension's trailing edge. Rounding has been found to enhance the reduction of low frequency noise while inhibiting an increase in high frequency noise. Increased high frequency noise has been a characteristic of the previous sharp edged devices even though they have reduced low frequency noise and have had a net acoustic benefit. Rounding has also been found to reduce the thrust loss of the previous sharp edged devices.
  • BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWING
  • [0005]
    [0005]FIG. 1 is a perspective view of a jet engine segmented mixing device with external plug nacelle;
  • [0006]
    [0006]FIG. 2 is illustrative of a jet engine segmented mixing device with internal plug nacelle;
  • [0007]
    [0007]FIG. 3 is illustrative of a jet engine segmented mixing device with mixed flow nacelle;
  • [0008]
    [0008]FIG. 4 is a triangular planform showing of a segmented mixing device on a nozzle sleeve;
  • [0009]
    [0009]FIG. 4A is a sectional view, taken along the lines 4A-4A of FIG. 4, showing in more detail how the surfaces of the mixing device extensions curve inward towards the engine center line;
  • [0010]
    [0010]FIG. 4B is a sectional view, taken along the lines 4B-4B of FIG. 4, showing in more detail how the extensions create a stream wise vortex;
  • [0011]
    [0011]FIG. 5 is a trapezoidal planform showing of a segmented mixing device on a nozzle sleeve;
  • [0012]
    [0012]FIG. 6 is illustrative of stream wise vortex flow;
  • [0013]
    [0013]FIG. 7 is illustrative of a jet engine with a segmented mixing device attached to a core compartment vent;
  • [0014]
    [0014]FIG. 8 is illustrative of an aircraft wing with a segmented mixing device in the slot between fore and aft airfoils.
  • DETAILED DESCRIPTION OF THE INVENTION
  • [0015]
    The present invention comprises a segmented mixing device which, when applied to the nozzle of a jet engine or surfaces of an aircraft, enhances mixing between adjacent flows and reduces the noise radiated from the jet's exhaust flow and the flow adjacent to the devices on the aircraft. The device does so with a very small degradation in aircraft performance when attached to the jet's primary nozzles. When the device is attached to secondary nozzles or vents or slotted airfoils, an improvement in engine or aircraft performance can result. The mixing device is a segmented, triangular or trapezoidal shaped, curved extension 1 to a nozzle's sleeve or surface trailing edge which results in a serrated trailing edge (see FIGS. 1, 2, 3, 7, and 8). This invention comprises: 1) A modification from the sharp pointed, triangular shaped, nozzle extensions evaluated in the hereinafter referenced NASA AST program to a semi-round, triangular or trapezoidal shaped planform (see FIGS. 4 and 5). 2) An application of the present nozzle extensions to internal and external plug primary nozzles of dual flow exhaust systems (see FIGS. 1 and 2). 3) An application of the nozzle extensions to secondary nozzles of dual flow exhaust systems (see FIGS. 1 and 2). 4) An application of the nozzle extensions to the nozzle of mixed flow exhaust systems and the flow splitter between the primary and secondary streams of those systems (see FIG. 3). 5) An application of the nozzle or surface extensions to vents in exhaust systems (see FIG. 7). And, 6) an application of the surface extensions to the trailing edge of any surface separating adjacent flows wherein enhanced mixing is desired (as an example, see FIG. 8).
  • [0016]
    The purpose of the present nozzle or surface extensions 1 is to enhance the natural free mixing of the adjacent flows and to reduce the acoustic energy associated with the velocity differences between the streams in which they are imbedded. The presently configured nozzle or surface extensions enhance the natural free mixing between adjacent streams by forcing the adjacent flows to penetrate into one another to a greater depth than that achievable with free mixing and therefore results in a more uniform flow in a shorter stream wise distance. The acoustic benefit of the extensions increases as the velocity differences between the streams increase. Two methodologies are employed to enhance mixing: 1) The surfaces of the extensions curve inward towards the engine centerline forcing the secondary (outer) flow into the primary (inner) flow (see FIG. 4A). 2) The extensions have a planform shape that creates a stream wise vortex that also enhances rapid mixing of the two streams (see FIG. 4B and FIG. 6). For extensions attached to nozzles, the circumferential shape of the extension's surface is an arc with a radius equal to the distance from the nozzle centerline to the extension's surface, i.e. an axisymetric surface (see FIG. 4B). Outward turned segments can also be used to enhance mixing. However, the thrust loss for outward turned segments on nozzles has been greater than that for inward turned segments. The present concept also includes rounding to outward turned segments.
  • [0017]
    Unlike the previous NASA AST configurations and the A. D. Young et al configurations described in U.S. Pat. No. 3,153,319, the extensions defined herein incorporate a planform with semi-rounded intersections 2 with the baseline nozzle and semi-round trailing edges 3. The purpose of the upstream rounding is to increase the strength of the stream wise vortex by allowing the primary (inner) flow to exit the nozzle sooner and in a more radial manner. Rounding the upstream intersection also eliminates the stress concentrations and low fatigue life of the previous NASA AST and A. D. Young et al concepts. Rounding the extension's trailing edge separates the two stream wise vortexes and increases the circumferential surface area available for the secondary (outer) flow to penetrate the primary (inner) flow. In addition, rounding the trailing edge increases the span-wise average turning angle, 0 (see FIG. 4A), of the secondary flow resulting in greater penetration of the secondary flow into the primary flow and increased mixing of the two flows. Rounding has been found to enhance the reduction of low frequency noise while inhibiting an increase in high frequency noise. The increase in high frequency noise has been a characteristic of the previous designs. Rounding has also been found to reduce the thrust loss of sharp pointed or small radiused nozzle extensions. The nozzle or surface extensions may vary in length, width, curvature, and count being only constrained by the geometry of the baseline nozzle or the surface to which they are attached.
  • [0018]
    In addition to using segmented surface extensions to reduce noise, they can be used to reduce drag on surfaces downstream of the segments when those surfaces are scrubbed by the flow that is adjacent to the segments. This is especially beneficial when the flow scrubbing the downstream surface has the lower energy level of the two adjacent flows. The drag reduction is achieved through mixing of the flows adjacent to the segments and the action of the vortexes emanating from the segments. Mixing increases the energy level (total pressure) of the flow having the lowest energy adjacent to the segments. The segmented extensions mix the two flows more rapidly than that achieved with natural free mixing. The enhanced mixing energizes the low energy flow so that it can overcome adverse pressure gradients on the downstream surface. One example of such an application is the flow exiting the core compartment of a jet engine (see FIG. 7). Typically, core compartment flow has a low total pressure relative to ambient, exits through a vent (nozzle), and separates from downstream surfaces when those surfaces encounter higher than ambient pressures. By attaching segments to the outer surface of the vent, the core compartment flow can mix with the adjacent high-energy flow, typically fan flow, and achieve a higher energy (total pressure) in a much shorter distance from the vent than that achieved by natural free mixing. As a result, flow separation on the downstream surface is prevented. Aircraft wings incorporating slots 5 or flaps 6 is another application where drag benefits can be achieved by incorporating segmented surface extensions 1 into the slot between the fore 7 and aft 6 airfoil (see FIG. 8). The vortexes shed from the segments attached to the trailing edge of the upstream airfoil along with the energized slot flow can prevent or delay separation on the aft airfoil, reducing the drag and increasing the lift of the wing. On multi-slotted airfoils, the segmented surface extensions can be incorporated into each slot.
  • [0019]
    The segmented extension creates vortexes by immersing the tip of the extension into the adjacent flow, a methodology for creating vortexes to mix flow and reduce noise and drag. In addition, the segmented nozzles described herein are cheaper to construct than nozzles of prior art since they can be axisymetric.
  • REFERENCES
  • [0020]
    1. D. C. Kenzakowski, J. Shipman, S. M. Dash, J. E. Bridges, and N. H. Saiyed, AIAA-2000-0219, “Turbulence Model Study of Laboratory Jets with Mixing Enhancements for Noise Reduction”, January 2000.
  • [0021]
    2. A. D. Young et al, U.S. Pat. No. 3,153,319, “Jet Noise Suppression Means”, Oct. 20, 1964.
Patent Citations
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Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US73058179 Feb 200411 Dec 2007General Electric CompanySinuous chevron exhaust nozzle
US75813847 Jun 20071 Sep 2009SnecmaTurbomachine nozzle cover provided with triangular patterns having a point of inflexion for reducing jet noise
US9511873 *9 Mar 20126 Dec 2016The Boeing CompanyNoise-reducing engine nozzle system
US9617954 *24 Sep 201211 Apr 2017SnecmaPrimary cowl of a turbofan comprising a rotating ring having micro-jets
US20130232948 *9 Mar 201212 Sep 2013The Boeing CompanyNoise-Reducing Engine Nozzle System
US20140245715 *24 Sep 20124 Sep 2014SnecmaPrimary cowl of a turbofan comprising a rotating ring having micro-jets
EP1873389A1 *7 Jun 20072 Jan 2008SnecmaTurbomachine nozzle cowl with triangular noise suppression tabs having an inflexion point
EP2636878A111 Mar 201311 Sep 2013The Boeing CompanyNoise-reducing engine nozzle system
Classifications
U.S. Classification60/204, 60/262
International ClassificationF02K1/48, F02K1/38
Cooperative ClassificationF05D2250/183, F05D2250/11, F05D2250/13, F05D2250/71, F05D2260/96, B64D33/06, F02K1/48, F02K1/386
European ClassificationF02K1/48, F02K1/38C, B64D33/06
Legal Events
DateCodeEventDescription
11 Jun 2003ASAssignment
Owner name: BOEING COMPANY, THE, ILLINOIS
Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:BALZER, RONALD L.;REEL/FRAME:014173/0876
Effective date: 20030530
28 Dec 2009FPAYFee payment
Year of fee payment: 4
27 Dec 2013FPAYFee payment
Year of fee payment: 8
27 Dec 2017MAFP
Free format text: PAYMENT OF MAINTENANCE FEE, 12TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1553)
Year of fee payment: 12